Accession Number : ADA243912


Title :   An Experimental Study of a Sting-Mounted Circulation Control Wing


Descriptive Note : Master's thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING


Personal Author(s) : Lacher, Steven J


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a243912.pdf


Report Date : Dec 1991


Pagination or Media Count : 136


Abstract : This wind tunnel study investigated the lift, drag, and pitching moment of a 20% thick, 8.5% camber, partial elliptical cross-section, single blowing slot, 2.325 aspect ratio, rectangular circulation control wing. The AFIT 5-foot wind tunnel was used. Lift and drag were referenced to the wind axis. The Reynolds number was 500,000 for all tests. Angle of attack was varied from -6 to 16 degrees and the effects of pulsed blowing were investigated. Effects of tripping the Coanda jet with a small flow barrier attached spanwise along the Coanda surface were also studied. Results indicate that there is a limit on maximum lift obtainable by increasing circulation. The limit is presumed to be the result of three-dimensional effects. Pulsed blowing has little effect on average lift, but results in violent oscillation of the wing as the sting physically bends under cyclic loading. In certain situations, tripping the Coanda jet may reduce drag without decreasing lift.


Descriptors :   *CONTROL , PITCH(MOTION) , LOADS(FORCES) , WIND , MOMENTS , ANGLE OF ATTACK , CYCLES , SURFACES , THREE DIMENSIONAL , PULSES , CROSS SECTIONS , RECTANGULAR BODIES , BARRIERS , SLOTS , FLOW , DRAG , WINGS , LIFT , OSCILLATION , CIRCULATION , WIND TUNNELS , REYNOLDS NUMBER , ELLIPSES , COANDA EFFECT


Subject Categories : Aerodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE